Conceptual Design Of A Supersonic Business Jet Propulsion System ... NASA/TM-2002-211797 ... National Aeronautics And Space Administration ... August 2002 PDF Download
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Languages : en
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721526901
Category :
Languages : en
Pages : 30
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NASA's Ultra-Efficient Engine Technology Program (UEETP) is developing a suite of technology to enhance the performance of future aircraft propulsion systems. Areas of focus for this suite of technology include: Highly Loaded Turbomachinery, Emissions Reduction, Materials and Structures, Controls, and Propulsion-Airframe Integration. The two major goals of the UEETP are emissions reduction of both landing and take-off nitrogen oxides (LTO-NO(x)) and mission carbon dioxide (CO2) through fuel burn reductions. The specific goals include a 70 percent reduction in the current LTO-NO(x) rule and an 8 percent reduction in mission CO2 emissions. In order to gain insight into the potential applications and benefits of these technologies on future aircraft, a set of representative flight vehicles was selected for systems level conceptual studies. The Supersonic Business Jet (SBJ) is one of these vehicles. The particular SBJ considered in this study has a capacity of 6 passengers, cruise Mach Number of 2.0, and a range of 4,000 nautical miles. Without the current existence of an SBJ the study of this vehicle requires a two-phased approach. Initially, a hypothetical baseline SBJ is designed which utilizes only current state of the art technology. Finally, an advanced SBJ propulsion system is designed and optimized which incorporates the advanced technologies under development within the UEETP. System benefits are then evaluated and compared to the program and design requirements. Although the program goals are only concerned with LTO-NO(x) and CO2 emissions, it is acknowledged that additional concerns for an SBJ include take-off noise, overland supersonic flight, and cruise NO(x) emissions at high altitudes. Propulsion system trade-offs in the conceptual design phase acknowledge these issues as well as the program goals. With the inclusion of UEETP technologies a propulsion system is designed which performs at 81% below the LTO-NO(x) rule, and reduces fuel burn by 23 percent co
Author: Robert J. Bruckner
Publisher:
ISBN:
Category :
Languages : en
Pages : 10
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Author: National Research Council
Publisher: National Academies Press
ISBN: 9780309058780
Category : Technology & Engineering
Languages : en
Pages : 168
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The National Aeronautics and Space Administration (NASA) is currently developing advanced technologies to form the foundation for the next breakthrough in civil aviation: an economically viable, environmentally acceptable supersonic transport. NASA's High Speed Research Program works in conjunction with industry to identify and address critical technological challenges to initiating commercial development of a practical supersonic transport. The key technical areas investigated are engine emissions, fuel efficiency, service life, and weight; community noise; aircraft range and payload; and weight and service life of airframe structures. Areas of particular interest include the ability of technologies under development to meet program goals related to noise, emissions, service life, weight, range, and payload. This book examines aircraft design requirements, assesses the program's planning and progress, and recommends changes that will help the program achieve its overall objectives.
Author: Egbert Torenbeek
Publisher: John Wiley & Sons
ISBN: 1119667046
Category : Technology & Engineering
Languages : en
Pages : 168
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Provides comprehensive coverage of how supersonic commercial aircraft are designed This must-have guide to conceptual supersonic aircraft design provides a state-of-the art overview of the subject, along with expert analysis and discussion. It examines the challenges of high-speed flight, covers aerodynamic phenomena in supersonic flow and aerodynamic drag in cruising flight, and discusses the advantages and disadvantages of oblique wing aircraft. Essentials of Supersonic Commercial Aircraft Conceptual Design is intended for members of a team producing an initial design concept of an airliner with the capability of making supersonic cruising flights. It begins with a synopsis of the history of supersonic transport aircraft development and continues with a chapter on the challenges of high-speed flight, which discusses everything from top level requirements and cruise speed requirements to fuel efficiency and cruise altitude. It then covers weight sensitivity; aerodynamic phenomena in supersonic flow; thin wings in two-dimensional flow; flat wings in inviscid supersonic flow; aerodynamic drag in cruising flight, and aerodynamic efficiency of SCV configurations. The book finishes with a chapter that examines oblique wing aircraft. Provides supersonic aircraft designers with everything they need to know about developing current and future high speed commercial jet planes Examines the many challenges of high-speed flight Covers aerodynamic phenomena in supersonic flow and aerodynamic drag in cruising flight Discusses the advantages and disadvantages of oblique wing aircraft Essentials of Supersonic Commercial Aircraft Conceptual Design is an ideal book for researchers and practitioners in the aerospace industry, as well as for graduate students in aerospace engineering.
Author: National Research Council
Publisher: National Academies Press
ISBN: 0309082773
Category : Technology & Engineering
Languages : en
Pages : 128
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Book Description
High-speed flight is a major technological challenge for both commercial and business aviation. As a first step in revitalizing efforts by the National Aeronautics and Space Administration (NASA) to achieve the technology objective of high-speed air travel, NASA requested the National Research Council (NRC) to conduct a study that would identify approaches for achieving breakthroughs in research and technology for commercial supersonic aircraft. Commercial Supersonic Technology documents the results of that effort. This report describes technical areas where ongoing work should be continued and new focused research initiated to enable operational deployment of an environmentally acceptable, economically viable commercial aircraft capable of sustained supersonic flight, including flight over land, at speeds up to approximately Mach 2 in the next 25 years or less.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781726163439
Category :
Languages : en
Pages : 40
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Ongoing human-response studies of sonic-boom noise indicated that a previous level of 1.0 psf might still be too annoying. This led to studies of a Supersonic Business Jet (SBJ), which might generate lower, more acceptable ground overpressures. To determine whether methods for designing a High Speed Civil Transport (HSCT) could be successfully applied, a SBJ concept was designed at the langley Research Center. It would cruise at Mach 2, carry 10 passengers for 4000 nautical miles, and generate a 0.50 psf or less on the ground under the flight path at start of cruise. Results indicated that a 10-passenger, low-boom SBJ design was just as technically demanding as a 300-passenger, low-boom HSCT design. In this report, the sources of these technical problems are identified, and ideas for addressing them are discussed.Mack, Robert J.Langley Research CenterSONIC BOOMS; SUPERSONIC TRANSPORTS; AIRCRAFT DESIGN; SUPERSONIC JET FLOW; CIVIL AVIATION; HUMAN REACTIONS; PASSENGERS...
Author: F. Edward McLean
Publisher:
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 216
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"This document provides a historic perspective of supersonic cruise technology, beginning with the early NACA supersonic research and including efforts during the B-70 and SST phase. It also records technological progress made in the NASA SCR and VCE programs." -- Foreward.
Author: Martin Schuermann
Publisher: Cuvillier Verlag
ISBN: 373698278X
Category : Technology & Engineering
Languages : en
Pages : 162
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The Preliminary Aircraft Design and Optimisation tool, PrADO, is an in-house program of the Institute of Aircraft Design and Lightweight Structures, TU Braunschweig, Germany, which covers a wide range of aspects of aircraft preliminary design. An initial aircraft concept serves as a basis for various analysis modules. Each module is designated to fulfil one special task e.g. aerodynamic analysis, estimation of structural mass, etc. The available methods grouped within those modules range from statistical methods to physics based models. From an aircraft developer’s point of view PrADO is used within both, the conceptual and the preliminary design phase. The aim of this thesis is to introduce methods and methodologies to aircraft conceptual and preliminary design, more precisely to PrADO, that allow to judge supersonic aircraft concepts. Therefore, the aerodynamic analysis module, the structural analysis module and the propulsion module are extended. An inviscid flow solver is integrated to obtain aerodynamic coefficients. The calculated data serves as input to other analysis modules of PrADO. While the aerodynamic analysis module solely uses the outer geometry of the aircraft, the structural analysis module uses its internal structural layout as additional input to a herein developed finite element model generator. The distribution of secondary mass, fuel loading and payload distributions as well as loads for ground cases and trimmed flight cases are taken from the PrADO database, whereas the aerodynamic forces are calculated by solving the inviscid Euler equations. The model serves as basis for structural sizing and consequently the estimation of structural mass. The purpose of the propulsion module is to size the engine, to calculate the engine performance map and to provide reliable mass data based on the thermodynamic cycle. PrADO provides various models for the analysis of turbojet, turbofan and turboprop engines. It is extended by a turbofan engine with mixed exhaust flow. The verification of the aerodynamic data is solely based on its expected qualitative distribution, since data from higher order methods was not available for the time being. The results compare well with the expected behaviour. The structural sizing process is verified based on an example from literature. The results of the developed sizing algorithm show extraordinary agreement with the reference data. The extended aircraft design process is finally applied to an aircraft from the European research project HISAC. The results compare well with global aircraft data. An excursion into the field of temperature effects in supersonic flight is provided, since no relevant literature is found on the topic with regard to conceptual and preliminary aircraft design. The results are translated into helpful information on the material selection process in the stage of aircraft pre-design. Eventually, the tool chain is applied to analyse a supersonic business jet and the results are presented. Based on the results of this basic design, a parameter study is conducted. A combination of cruise Mach number and design range is varied. Global design parameters show expected sensitivity to such variations. Das am Institut für Flugzeugbau und Leichtbau der TU Braunschweig entwickelte Programm PrADO (Preliminary Aircraft Design and Optimisation tool) stellt Werkzeuge zur Analyse und Beurteilung von Flugzeugen in der Konzept- und Vorentwurfsphase bereit. Basis der Analyse ist ein erstes Flugzeugkonzept. Jedes Entwurfsmodul gruppiert Methoden zur Lösung einer Teilaufgabe im Vorentwurfsprozess, z.B. Bestimmung der aerodynamischen Beiwerte oder Masseanalyse. Die vorhandenen Methoden reichen von einfachen Abschätzungsformeln bis hin zu physikalisch begründeten Berechnungsmodellen. Die Zielsetzung dieser Arbeit ist es, Methoden in die Konzept- und Vorentwurfsphase, genauer in das Programm PrADO, einzuführen, welche die Bewertung von Überschallflugzeugen ermöglichen. Daher werden die aerodynamischen, strukturmechanischen und antriebsspezifischen Entwurfsmodule erweitert. Zur Berechnung der aerodynamischen Beiwerte wird ein Euler-Verfahren eingesetzt. Die Ergebnisse stehen anderen Entwurfsmodulen in Form von Kennfeldern zur Verfügung. Das strukturmechanische Modell benötigt, neben der äußeren Geometrie, auch den inneren Aufbau des Flugzeugs. Diese Daten bilden die Grundlage eines Finite-Elemente-Modells. Die Verteilung von Sekundärmassen, Kraftstoff und Nutzlast, sowie Lasten für Boden- und ausgetrimmte Flugfälle werden der PrADO-Datenbank entnommen. Die aerodynamischen Kräfte werden mit dem Euler-Verfahren berechnet und auf das Modell aufgeprägt. Das Modell bildet die Basis zur Strukturdimensionierung und somit der Berechnung der Strukturmasse. Die Aufgabe des Antriebsmoduls ist die Triebwerksgröße zu bestimmen, Triebwerkskennfelder bereitzustellen und die Masse des Antriebssystems zu berechnen. Das Modul wird um ein Zweikreis-Turbinenluftstrahltriebwerk mit Mischung von Primär- und Sekundärstrom ergänzt. Die qualitativen Verläufe der aerodynamischen Beiwerte entsprechen dem zu erwartenden Verhalten. Für einen quantitativen Vergleich stehen keine Vergleichsdaten aus höherwertigen Verfahren zur Verfügung. Das erweiterte Strukturanalysemodul wird auf ein Literaturbeispiel angewendet. Die Ergebnisse zeigen eine sehr gute Übereinstimmung mit den Daten. Nach der Verifikation der Einzelmodule wird der Gesamtentwurfsprozess an einem Flugzeug des europäischen Projekts HISAC überprüft. Die globalen Entwurfsergebnisse zeigen sehr gute Übereinstimmungen mit den verfügbaren Referenzdaten. Die im Überschallflug auftretenden thermischen Aspekte werden in einem kurzen Exkurs behandelt. Dies erscheint notwendig, da zu diesem Thema keine, auf den Vorentwurf bezogene Literatur gefunden wurde. Die Ergebnisse geben dem Ingenieur erste Hinweise zur Materialauswahl im Rahmen der Konzept- und Vorentwurfsphase. Schlussendlich wird der erweiterte Entwurfsprozess zum Entwurf eines Überschallgeschäftsreiseflugzeugs genutzt. Auf Basis der gewonnenen Erkenntnisse wird eine Parameterstudie durchgeführt. Die Sensitivitäten der globalen Entwurfsparameter bei Änderungen von Machzahl und Reichweite werden gut wiedergegeben.
Author: Herbert F. Hardrath
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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